EP0186794A1 - Dispositif pour la fixation en position d'arrêt de barres d'une longueur fixe - Google Patents

Dispositif pour la fixation en position d'arrêt de barres d'une longueur fixe Download PDF

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Publication number
EP0186794A1
EP0186794A1 EP85115255A EP85115255A EP0186794A1 EP 0186794 A1 EP0186794 A1 EP 0186794A1 EP 85115255 A EP85115255 A EP 85115255A EP 85115255 A EP85115255 A EP 85115255A EP 0186794 A1 EP0186794 A1 EP 0186794A1
Authority
EP
European Patent Office
Prior art keywords
rod
arm
shaft
support
bracket
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP85115255A
Other languages
German (de)
English (en)
Other versions
EP0186794B1 (fr
Inventor
Daniel H. Zeorlin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Boeing Co filed Critical Boeing Co
Publication of EP0186794A1 publication Critical patent/EP0186794A1/fr
Application granted granted Critical
Publication of EP0186794B1 publication Critical patent/EP0186794B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/08—Inspection panels for power plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings

Definitions

  • the present invention relates to mounting brackets, and more particularly to receiver for securing the free end of a fixed length rod when the latter is not in active use.
  • Aircraft are commonly provided with elongated, rigid support members which serve to hold the engine cowling open when access into the engine compartment is required.
  • the members or support rods are mounted at one end to the interior of a cowl section usually by a universal joint, to permit ready movement of the member into the cowl supporting position.
  • the "free" end of the rod is often connected to a fixed structure such as to some part of the engine frame so that the support holds the cowl open preventing against inadvertent closure and consequent damage or personal injury.
  • the support rod When not in use, the support rod is swung to a stowed position lying generally alongside the interior surface of the cowling. It is highly important that the rod be securely fastened against accidental dislodgement when in this stowed position. It is also equally important that any tendency for the rod to vibrate when the engine is in operation be eliminated.
  • the present invention provides a bracket for releaseably securing the free end of a fixed length rod mounted for swinging movement about a pivot point spaced longitudinally of the rod, said bracket comprising: a support adapted to be mounted in fixed position adjacent the path of swinging movement of said rod free end; an arm pivotally coupled to the support; means carried by the arm and adapted to cooperate with the rod free end for releaseably securing the latter to the arm, said arm being swingable with respect to the support to move the securing means toward and away from the rod pivot point and into and out of engagement with the rod free end; and spring means operably coupled with the support and the arm respectively for yieldably biasing the arm toward the rod pivot point, whereby the rod and arm may be manually swung to respective positions of mutual engagement of the rod free end and the securing means for releaseably securing the rod in said position.
  • Still another object of the present invention is to provide a rod capable of achieving the aforestated objectives, yet which is constructed in a manner which lends itself to quick and easy operator manipulation for installation and removal of the rod to and from its bracket mounted position.
  • Figures 1 and 2 of the drawing illustrate a typical cowling 10 comprised of a pair of cowl sections 12 and 14 which are hinged to an aircraft for movement between the full line positions and the dash line positions shown in Fig. 1.
  • the sections When the sections are in the full line positions, they are in covering relationship over an engine 16. Movement of each section to its dash line position provides access to the engine compartment as may be required for engine service and maintenance operations and the like.
  • Suitable hinge structure is, of course, provided for connecting the cowl sections to the aircraft. Inasmuch as such structure forms no part of the instant invention, it need not be illustrated or described in detail.
  • each of the individual cowl sections is held in its opened position by means of its respective elongated, rigid support rod 18 which is manually interposed between the engine and the cowl section.
  • One end of each rod 18 is typically mounted for swinging movement to the interior surface of its corresponding cowl section and the free end of the rod is adapted to be releaseably connected to a peripherally extending engine flange 20, thereby holding the corresponding section in its opened position:
  • the rods 18 are carried in the stowed or standby positions lying generally parallel with the inside surfaces of the respective cowl sections in the manner illustrated in dash dot lines in Fig. 1 and 2 of the drawing.
  • the cowl support rods and stowage brackets for each cowl section are identical, only one set will be described in detail.
  • the bracket comprising the subject matter of this invention is shown in conjunction with the support rod which it serves to secure in stowed position in Figs. 3 through 6 of the drawing.
  • the rod 18 comprises an elongated, rigid support member 22 having a universal joint 24 affixed to one end thereof.
  • U-joint 24 is, in turn, fixedly secured by a mounting element 25 to the internal surface of the aircraft cowl section 14 as illustrated in Fig. 3.
  • the end of rod 18 remote from U-joint 24 has a generally circular shaped head 26 having a notch 28 communicating with the extreme outermost end of the rod head and extending generally toward the center of the arcuate portion of the head as shown in the drawings.
  • Each side of head 26 has a rim 30 extending peripherally around the notch and tapered inwardly from the generally flat, parallel side faces of the head.
  • a collar 32 is telescoped over an offset portion 34 of member 22 proximal the free end of the rod. Collar 32 slides freely over the outer surface of portion 34 and is connected with an elongated, rigid locking plunger 36. Plunger 36 is received within a suitable bore (not shown) in head 26 communicating with notch 28.
  • Rod 18, including head 26 and its locking sleeve and plunger arrangement, is entirely conventional and forms no part of the present invention. It suffices to say that the rod is provided with an internal spring (not shown) associated with plunger 36 normally biasing the collar and plunger to the extreme outermost position thereof shown in Fig. 3 of the drawing.
  • plunger 36 permits the free end of rod 18 to be locked onto a shaft received within notch 28, such as would conventionally be installed on the engine flange 20 to hold the rod in the cowl supporting position.
  • the rod head 26 can be quickly and easily released from its locked position over a shaft of this type by manually sliding collar 32 against the bias of the internal spring to withdraw plunger 36 into the position thereof illustrated in Fig. 5 of the drawing. So long as the plunger is in its extended position, however, the extreme outermost end of the plunger closes the outermost end of notch 28 a sufficient amount to insure against inadvertent release of the rod head 26 from the shaft.
  • a mounting element incorporating a fixed shaft on engine flange 20 is entirely suitable for securing the free end of rod 18 in position to support the cowl section in its open position.
  • Slight variations in the fixed rod length as might occur from wear, temperature variations, or the like creates no substantial disadvantage because of the available relative movement between the swinging cowl section which carries the rod and the engine flange upon which the bracket is mounted in fixed location. Any such rod length variation would only minutely effect a variation in the extent to which the cowl section is held open by the rod. Such variations are too slight to be noticed and can have no adverse effect whatsoever on access to the engine compartment.
  • Bracket 38 comprises a support 40 including an elongated, rigid, substantially flat base plate 42 which is adapted to be fixedly secured to the interior surface of its corresponding cowl section, such as section 14, by rivets or the like.
  • Support 40 includes a pair of spaced apart, parallel ears 44 integral with base plate 42 and projecting upwardly therefrom.
  • Bracket 38 also includes an elongated, rigid arm 46 preferably formed from an initially flat sheet of material bent upon itself into generally transversely U-shaped configuration having a medial web 48 and a pair of spaced apart parallel flanges 50 extending parallel with the ears 44 of support 40.
  • the ears 44 are provided with apertures which are aligned with corresponding holes in the arm flanges 50 to receive an elongated axle in the form of a bolt 52 pivotally coupling the arm 46 to support 40 for swinging movement of the arm toward and away from the point of pivotal attachment of rod 18 to its fixed support 26.
  • the point of pivotal attachment of the rod to its support is, of course, defined by the intersection of the axes of pivoting movement of U-joint 24.
  • a tubular spacer 54 is telescoped over bolt 52 between the spaced apart arm flanges 50.
  • Bolt 52 projects outwardly beyond the respective ears 44 a sufficient distance to receive the coil sections 56 and 58 of a double torsion spring 60 in telescoped relationship over the projecting ends of the bolt as shown in the drawings.
  • One end of each spring section is integrally attached to the corresponding end of the other section so that these spring ends engage web 48 of arm 46.
  • the other ends of the respective spring sections are engaged against base plate 42 as illustrated best in Fig. 6 of the drawing.
  • spring 60 exerts a substantial, yet uniform biasing force tending to swing arm 46 about bolt 52 in a counterclockwise direction as illustrated in Fig. 3.
  • Suitable bearings may be interposed between the bolt and the spring sections and retaining washers may also be installed as illustrated in the drawings.
  • Means for securing the free end of a corresponding support rod 18 to bracket 38 comprises a shaft 62 having opposed ends secured to the corresponding proximal flanges 50 of arm 46 and spanning the distance therebetween.
  • Shaft 62 is preferably of transversely circular configuration and has a central portion 64 and a pair of enlarged, spaced apart end sections 66 and 68.
  • the end sections 66 and 68 respectively are tapered inwardly as illustrated in Fig. 6 so that the transverse diameter of the shaft increases as the respective outermost ends of the shaft are approached.
  • This taper provides a generally spool like configuration and the tapers of the sections 66 and 68 are configured to complementally engage the correspondingly tapered rims 30 on either side of the support rod head 26, as will be hereinafter more fully explained.
  • the cowl support rod 18 when disengaged from its cowl supporting position attached to the engine flange, is moved to the stowed position by swinging the free end of the rod into proximity with bracket 38.
  • the operator manually swings the bracket arm 46 in a clockwise direction as viewed in Fig. 3.
  • collar 32 of the rod is moved to the left withdrawing plunger 36 within the rod, thereby completely opening notch 28.
  • the spool like shaft 62 is engaged into the notch while the operator releases arm 46 and also releases sleeve 32 to permit plunger 36 to project into the notch, locking the rod to the bracket.
  • the operator can simultaneously grasp sleeve 32 while extending one or more fingers into engagement with arm 46 to effect the interconnection of the rod with the attaching bracket with one hand.
  • the collar 32 is shifted in the direction of the arrow in Fig. 5. Simultaneous upward swinging movement of the rod results in detachment of the rod from the bracket as the arm 46 of the latter is cammed out of the notch as will be readily understood.
  • bracket 38 wherein arm 46 is constantly biased toward the point of pivotal attachment of rod 18 to the cowl section prevents any looseness in the rod and bracket attachment which would lead to intolerable vibrations during operation of the aircraft.
  • the spool shape of shaft 62 which complementally engages the tapered rims of the rod head 26 insures that the head is firmly seated intermediate the adjacent arm flanges 50 and spaced from the latter to prevent rattling of the components. Any wear which may occur to rod head 26 is automatically compensated for by the bias of spring 60. This insures the snug fitting together of the components at all times.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Pivots And Pivotal Connections (AREA)
  • Vibration Prevention Devices (AREA)
EP85115255A 1984-12-03 1985-12-02 Dispositif pour la fixation en position d'arrêt de barres d'une longueur fixe Expired - Lifetime EP0186794B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US677568 1984-12-03
US06/677,568 US4627590A (en) 1984-12-03 1984-12-03 Stowage receiver for fixed length rod

Publications (2)

Publication Number Publication Date
EP0186794A1 true EP0186794A1 (fr) 1986-07-09
EP0186794B1 EP0186794B1 (fr) 1990-05-09

Family

ID=24719253

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85115255A Expired - Lifetime EP0186794B1 (fr) 1984-12-03 1985-12-02 Dispositif pour la fixation en position d'arrêt de barres d'une longueur fixe

Country Status (4)

Country Link
US (1) US4627590A (fr)
EP (1) EP0186794B1 (fr)
JP (1) JPS61180012A (fr)
DE (1) DE3577591D1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190063134A1 (en) * 2017-08-25 2019-02-28 MarathonNorco Aerospace Retention Device for a Hold Open Rod
EP3473549A1 (fr) * 2017-10-20 2019-04-24 Hamilton Sundstrand Corporation Actionneur avec atténuation de vibrations utilisant des matériaux visco-élastiques
CN110439707A (zh) * 2019-07-26 2019-11-12 中国航发沈阳发动机研究所 一种飞机尾部弹性片组件

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2337076A (en) * 1997-10-09 1999-11-10 Rajkrishan Fakirchand Sharma Automatic pipe clamp
FR2836963A1 (fr) * 2002-03-08 2003-09-12 Airbus France Dispositif de fixation d'un element sur une structure d'aeronef
US20040049994A1 (en) * 2002-07-02 2004-03-18 Hazenstab Robert E. Brace boot
FR3007739B1 (fr) * 2013-07-01 2016-02-05 Aircelle Sa Dispositif d’assistance pour la manœuvre d’un capot et nacelle de turboreacteur ainsi equipee
US10815708B2 (en) * 2017-07-06 2020-10-27 Porter Systems Positioner mechanism using linear adjusting lock

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE59946C (de) * J. louis in Brüssel, 14. Rue de l'artifice Karabinerhaken mit federndem Verschlufsschieber
DE1077086B (de) * 1954-08-04 1960-03-03 Renault Vorrichtung zum Festhalten einer um eine waagerechte Achse vertikal schwenkbaren Motorhaube oder Kofferraumhaube eines Kraftfahrzeugs
FR1518383A (fr) * 1966-04-15 1968-03-22 Norco Dispositif d'accrochage détachable à tubes concentriques
DE1937764A1 (de) * 1969-07-25 1971-02-11 Kloeckner Humboldt Deutz Ag Fanghaken,insbesondere fuer den oberen Lenker einer Geraeteanbauvorrichtung
DE1939215A1 (de) * 1969-08-01 1971-02-11 Norco Inc Schnell loesbare Universal-Bewegungs-Kupplung

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1621630A (en) * 1925-11-19 1927-03-22 Debus Sander Box fastener
US2091651A (en) * 1936-05-06 1937-08-31 Platt Benjamin Partition holder for luggage carriers
US2178998A (en) * 1938-04-12 1939-11-07 Curtiss Wright Corp Engine cowling
US2741505A (en) * 1954-06-07 1956-04-10 Gen Motors Corp Door fastener
US2929650A (en) * 1956-10-31 1960-03-22 Midwest Mfg Corp Refrigerator door lock
US3117689A (en) * 1962-10-16 1964-01-14 Sr Anthony M Dedic Prop for trunk compartment lids
US3225856A (en) * 1963-10-01 1965-12-28 Gen Motors Corp Safety hinge and latch for a vehicle body closure
DE2853399A1 (de) * 1978-12-11 1980-06-19 Scharwaechter Gmbh Co Kg Von den tuerscharnieren unabhaengiger tuerfeststeller
GB2123472B (en) * 1982-05-11 1985-10-30 Clarke Instr Limited Electromagnetic lock

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE59946C (de) * J. louis in Brüssel, 14. Rue de l'artifice Karabinerhaken mit federndem Verschlufsschieber
DE1077086B (de) * 1954-08-04 1960-03-03 Renault Vorrichtung zum Festhalten einer um eine waagerechte Achse vertikal schwenkbaren Motorhaube oder Kofferraumhaube eines Kraftfahrzeugs
FR1518383A (fr) * 1966-04-15 1968-03-22 Norco Dispositif d'accrochage détachable à tubes concentriques
DE1937764A1 (de) * 1969-07-25 1971-02-11 Kloeckner Humboldt Deutz Ag Fanghaken,insbesondere fuer den oberen Lenker einer Geraeteanbauvorrichtung
DE1939215A1 (de) * 1969-08-01 1971-02-11 Norco Inc Schnell loesbare Universal-Bewegungs-Kupplung

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190063134A1 (en) * 2017-08-25 2019-02-28 MarathonNorco Aerospace Retention Device for a Hold Open Rod
EP3473549A1 (fr) * 2017-10-20 2019-04-24 Hamilton Sundstrand Corporation Actionneur avec atténuation de vibrations utilisant des matériaux visco-élastiques
CN110439707A (zh) * 2019-07-26 2019-11-12 中国航发沈阳发动机研究所 一种飞机尾部弹性片组件

Also Published As

Publication number Publication date
US4627590A (en) 1986-12-09
EP0186794B1 (fr) 1990-05-09
JPS61180012A (ja) 1986-08-12
DE3577591D1 (de) 1990-06-13

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